EP3771864A1 - Lance pour deux carburants dotée de microcanaux de refroidissement - Google Patents

Lance pour deux carburants dotée de microcanaux de refroidissement Download PDF

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Publication number
EP3771864A1
EP3771864A1 EP19208960.5A EP19208960A EP3771864A1 EP 3771864 A1 EP3771864 A1 EP 3771864A1 EP 19208960 A EP19208960 A EP 19208960A EP 3771864 A1 EP3771864 A1 EP 3771864A1
Authority
EP
European Patent Office
Prior art keywords
conduit
lance
cooling
disposed
microchannels
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP19208960.5A
Other languages
German (de)
English (en)
Other versions
EP3771864B1 (fr
Inventor
Andre Theuer
Nico Biagioli
Mario Pudrlja
Rohit Madhukar Kulkarni
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
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Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Publication of EP3771864A1 publication Critical patent/EP3771864A1/fr
Application granted granted Critical
Publication of EP3771864B1 publication Critical patent/EP3771864B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D17/00—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel
    • F23D17/002—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel gaseous or liquid fuel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/36—Supply of different fuels
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/35—Combustors or associated equipment
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/07021—Details of lances
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2204/00—Burners adapted for simultaneous or alternative combustion having more than one fuel supply
    • F23D2204/10—Burners adapted for simultaneous or alternative combustion having more than one fuel supply gaseous and liquid fuel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2209/00—Safety arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03341—Sequential combustion chambers or burners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube
    • F23R3/08—Arrangement of apertures along the flame tube between annular flame tube sections, e.g. flame tubes with telescopic sections
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow

Definitions

  • a lance for a burner includes an innermost conduit defining a first fluid passage and a plurality of first fuel injection channels, each first fuel injection channel terminating at a first outlet; an intermediate conduit circumferentially surrounding the innermost conduit, the intermediate conduit defining a second fluid passage and a plurality of second fuel injection channels, each second fuel injection channel terminating at a second outlet; an outermost conduit circumferentially surrounding the intermediate conduit, the outermost conduit defining a third fluid passage, a plurality of third air outlets through the outermost conduit and surrounding the first outlets, a plurality of fourth air outlets through the outermost conduit and surrounding the second outlets, and a plurality of cooling microchannels; wherein each cooling microchannel includes and extends between a microchannel inlet in fluid communication with the third fluid passage and a microchannel outlet on an outer surface of the outermost conduit.
  • the additive manufacturing process includes the DMLM process.
  • the DMLM process includes providing and depositing a metal alloy powder to form an initial powder layer having a preselected thickness and a preselected shape.
  • a focused energy source i.e., a laser or electron beam
  • small air inlets e.g., 202
  • cooling microchannels e.g., 200
  • FIGS. 6 and 7 also illustrate a third set of microchannels 220, which have air inlets 222 disposed in alternating arrangement between the air outlets 214 of the second set of microchannels 210 or between the microchannels 210 having the air outlets 216.
  • the air inlets 222 are disposed on the inward surface of the body 102, while the air outlets 214, 216 are disposed on the outer surface of the body 102.
  • the air inlets 222 are disposed in the same general plane proximate to the joint 145.
  • the microchannels 220 may be of different lengths to optimize the cooling flow around the joint 145 and the corner of the body 102, thus resulting in air outlets 224 in different planes.
  • the outlets 224 may be seen in FIG. 3 .
  • FIGS. 5 , 6 , and 11 illustrate a fourth set of cooling microchannels 230 that extend along the curved lower surface 124 of the downstream portion 120 of the lance 100.
  • Each microchannel 230 extends between an air inlet 232 on an inner surface of the curved lower surface 124 and an air outlet 234 on an outer surface of the curved lower surface 124.
  • the outlet 234 of one such microchannel 230 may be seen in FIG. 3 .
  • FIGS. 5 , 6 , 12, and 13 illustrate a fifth set of cooling microchannels 240 that are disposed at the tip portion 130 of the lance 100.
  • the cooling microchannels 240 extend from an air inlet 242 disposed on an inner surface of the tip portion 130 to an air outlet 244 on the outer surface of the tip portion 130 (as shown in FIG. 5 ).
  • a self-centering fixation system 300 is disposed in the passage 174 between the outer surface of the intermediate conduit 160 and the inner surface of the outermost conduit 170.
  • the fixation system 300 which is located along the longitudinal axis 101 of the lance 100, permits movement of the conduits 160, 170 along the longitudinal axis 131 of the downstream portion 120 and the tip portion 130. Movement along the radial direction of the downstream portion 120 (and, therefore, along the longitudinal axis 101 of the lance 100) is prevented.
  • fixation system 300 is illustrated with four sets of hook-shaped elements 302-308 and T-shaped pegs 310, the number of sets may vary.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Gas Burners (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
EP19208960.5A 2018-08-30 2019-11-13 Lance pour deux carburants dotée de microcanaux de refroidissement Active EP3771864B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US201862724784P 2018-08-30 2018-08-30
US16/528,927 US11339968B2 (en) 2018-08-30 2019-08-01 Dual fuel lance with cooling microchannels

Publications (2)

Publication Number Publication Date
EP3771864A1 true EP3771864A1 (fr) 2021-02-03
EP3771864B1 EP3771864B1 (fr) 2022-09-28

Family

ID=69639634

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19208960.5A Active EP3771864B1 (fr) 2018-08-30 2019-11-13 Lance pour deux carburants dotée de microcanaux de refroidissement

Country Status (5)

Country Link
US (1) US11339968B2 (fr)
EP (1) EP3771864B1 (fr)
JP (1) JP7446742B2 (fr)
KR (1) KR20200026729A (fr)
CN (1) CN110873337A (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11774093B2 (en) * 2020-04-08 2023-10-03 General Electric Company Burner cooling structures
US11988386B2 (en) * 2021-12-03 2024-05-21 Honeywell International Inc. Gas turbine engine injector module with thermally coupled fuel lines having respective outlets
KR102607178B1 (ko) * 2022-01-18 2023-11-29 두산에너빌리티 주식회사 연소기용 노즐, 연소기 및 이를 포함하는 가스 터빈
US11572803B1 (en) 2022-08-01 2023-02-07 General Electric Company Turbine airfoil with leading edge cooling passage(s) coupled via plenum to film cooling holes, and related method

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2011054757A2 (fr) * 2009-11-07 2011-05-12 Alstom Technology Ltd Système d'injection pour brûleur de réchauffage avec lances à combustible
US8943831B2 (en) 2010-06-23 2015-02-03 Alstom Technology Ltd Lance of a burner
EP3076084A1 (fr) * 2015-03-30 2016-10-05 General Electric Technology GmbH Dispositif d'injecteur de carburant
EP3168535A1 (fr) * 2015-11-13 2017-05-17 General Electric Technology GmbH Corps de forme aérodynamique et procédé de refroidissement d'un corps placé dans un écoulement de fluide chaud

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5181379A (en) * 1990-11-15 1993-01-26 General Electric Company Gas turbine engine multi-hole film cooled combustor liner and method of manufacture
WO2007113074A1 (fr) * 2006-03-31 2007-10-11 Alstom Technology Ltd Lance a combustible pour installation de turbine a gaz et procede d'utilisation d'une lance a combustible
US8281594B2 (en) * 2009-09-08 2012-10-09 Siemens Energy, Inc. Fuel injector for use in a gas turbine engine
WO2011054760A1 (fr) * 2009-11-07 2011-05-12 Alstom Technology Ltd Système de refroidissement permettant d'accroître le rendement d'une turbine à gaz

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2011054757A2 (fr) * 2009-11-07 2011-05-12 Alstom Technology Ltd Système d'injection pour brûleur de réchauffage avec lances à combustible
US8943831B2 (en) 2010-06-23 2015-02-03 Alstom Technology Ltd Lance of a burner
EP3076084A1 (fr) * 2015-03-30 2016-10-05 General Electric Technology GmbH Dispositif d'injecteur de carburant
EP3168535A1 (fr) * 2015-11-13 2017-05-17 General Electric Technology GmbH Corps de forme aérodynamique et procédé de refroidissement d'un corps placé dans un écoulement de fluide chaud

Also Published As

Publication number Publication date
US11339968B2 (en) 2022-05-24
KR20200026729A (ko) 2020-03-11
CN110873337A (zh) 2020-03-10
JP7446742B2 (ja) 2024-03-11
US20200072469A1 (en) 2020-03-05
EP3771864B1 (fr) 2022-09-28
JP2020034269A (ja) 2020-03-05

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